A system and method for damage detection and for evaluating the real operation conditions for structural platforms using structural health monitoring is integrated to a system and method that permits for the platform to provide a flexible geometric control considering a self-adapting morphing which is capable of providing better operating structural platform performance.

A shape-morphing ultralight structure using materials that dramatically increase the efficiency of load-bearing aerostructures that includes a programmable material system applied as a large-scale, ultralight, and conformable (shape-morphing) aeroelastic structure. The use of a modular, lattice-based, ultralight material results in stiffness and density typical of an elastomer. This, combined with a building block-based manufacturing and configuration strategy, enables the rapid realization of new adaptive structures and mechanisms. The heterogeneous design with programmable anisotropy allows for enhanced elastic and global shape deformation in response to external loading, making it useful for tuned fluid-structure interaction. The present invention demonstrates an example application experiment using two building block types for the primary structure of a 4.27 m wingspan aircraft with spatially programed elastic shape morphing to increase aerodynamic efficiency.

Flexible control surfaces and related methods are disclosed. Example apparatus disclosed herein include an airfoil including a skin, the skin having perforations filled with an elastomer to increase a flexibility of the skin; and a flexible core adjacent the perforations of the skin to support the skin.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

Embodiments of the present invention relate to an adaptable wing having a variable geometry for influencing aerodynamic performance, the wing comprising a jointed leading edge having a main pivot, and a wrist joint, with a wing arm therebetween, and a distal wing hand depending from the wrist joint; the wing being reciprocally actuable, via the main pivot and wrist joint, between a first state having an extended wing planform and a second state having a tucked wing planform.

A method and apparatus for controlling movement of an aircraft. An aerodynamic function desired for controlling the movement of the aircraft at a particular altitude is identified. The aerodynamic function identified is part of a group of aerodynamic functions used to control the movement of the aircraft at a number of different altitudes. A group of inflatable blades is filled with a fluid to a pressure that corresponds to the aerodynamic function. The group of inflatable blades at the pressure has a shape and a group of dimensions that provide the aerodynamic function.

A morphing wing for an aircraft includes first and second structural ribs with four active members and four passive members connected therebetween. First and second active members and third and fourth active members attach at first and second positions. The first and third active members and the second and fourth active members attach at third and fourth positions. A first passive member connects between third and fifth positions. A second passive member connects between second and seventh positions. A third passive member connects between fourth and sixth positions. A fourth passive member connects between first and eighth positions. Adjustment of the four active members morphs the wing from a first configuration to a second configuration. The first and second positions are at corners of a first quadrilateral diagonally opposite to one another. The four passive members attach to the first structural rib at the corners of the first quadrilateral.

A system and method for damage detection and for evaluating the real operation conditions for structural platforms using structural health monitoring is integrated to a system and method that permits for the platform to provide a flexible geometric control considering a self-adapting morphing which is capable of providing better operating structural platform performance.

A structure, devices comprising such structures, methods and systems for designing structures is provided. As an example, a structure may include a plurality of first type members, each first type member corresponding to a respective first type vertex of an underlying aperiodic tiled lattice; a plurality of second type members, each second type member corresponding to a respective second type vertex of the underlying aperiodic tiled lattice; and a plurality of revolute joints corresponding to respective edges of the underlying aperiodic tiled lattice and connecting respective joint parts of pairs of members, each pair comprising a first type member and a second type member; wherein: each respective revolute joint is located, with respect to a local position of the respective edge, at a first common normalized vector with respect to a local position of the respective first type vertex and at a second common normalized vector with respect to a local position of the respective second type vertex.